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E. H. JUNGCLAS.

AIRCRAFT ANCHOR. APPLICATION FILED SEPT. I4. 1911.

Patented Sept. 23, 1919.

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AIRCRAFT-ANCHOR.

Specification of Letters Patent. Patented Sgpt, 23, 1919 Application filed September 14, 1917. Serial No. 191,369.

To all whom it may concern:

Be it knownthat I, EDWARD H. JUNooLAs, a citizen of the United States, and a resident Tn Figs. 2. and 4, the tension element comprises the forward tubular member and the member 9 sliding in the member S and held to themember 8 by a tension spring with the under side of the aeroplane body.

of Cincinnati, in the county of Hamilton 10 inside the member 8. A pointer 11 on so 5 and State of Ohio, have invented certain the member 9 extends out through a longitunew and useful Improvements in Aircraftdinal slot 12 in the member 8, and as it slides Anchors, of which the following is a sp'eoialong graduations 13 along the edge of the fi ti slot onthe outside of the member 8, indi- My invention relates to means for hold- Oates the pull of the aeroplane, so that an 5 1o ing aircrafts, especially aeroplanes, during operator may determine the tractive effort the operations preliminary to flight after of the craft as an indication of when to the propeller is started and exertinga pull release it. In the example ofFig. 3, the Onthe Craft tension element is a flexible cable 1'.

- The object of my invention is to enable the lVhlle the tension elements are thus modi- 70 15 aviator to dispense with assistants during fied, the releasable connecting devices 3 are such time, so that flight may be effected atpreferably the same; consisting as best any time or any place wherever the craft Shown in Fig. 5, of a bar 14 suitably conmay h li ht d, nected to the free end of the tension ele- My invention-consists in the combination {merit and extending up therefrom and hav- 75 of parts and in the details of construction 111g two jaws'15 extending back opposite and arrangement of parts as will hereinthe tension element connection and having. after be more fully described and claimed. at its upper end a backwardly extending lug In the drawings: i 16. Through this lug 16 and through the Figure l is a side elevation of an aero jaws 15 projects a plunger 17 which is norso plane anchored by a device embodying my mally held projected across the space beinvention; tween the jaws 15 by a helical 'spring18 Fig. 2 is apartial similar view somewhat around the plunger and compressed between enlarged and showing a modification of my a collar 19 fixed on the plunger and the i ti lower side of the. lug 16. The stake 4 has 85 Fig. 3 is a view similar to Fig. 2 showan eye-bolt 20 through it with its eye proing another modification of my invention; jecting forward between the jaws 15 and Fig. 4 is an enlarged detail partly inlonembracing the plunger 17. gitudinal section of the-yieldable connection Thus if the plunger 17 is withdrawn upand indicating means of Fig. 2.. wardly out of the eye of the eye-bolt 20, 90 Fig. 5 is a vertical longitudinal crossthe tension element is released from the section of the latch. stake leaving the aeroplane free to travel As shown in Fig. 1, a tension element 1 forward. has a pivotal connection or hinge 2 on the The upperend of the plunger 17 has an, lower'side of'the body of the aeroplane on eye 21 in which the cable 6 is fastened, 95

40 the fore-and-aft center line thereof. This which cable passes up over the sheave 7 to tension element 1 extends downwardly and the treadle 5 as hereinbefore described, and rearwardly and on its free end has a releasas fully shown in Fig. 1. Thus, it will be able connecting device or latch 3 which is seen that when the aviator pushes forward connected to a stake 4 driven into the ground on the treadle- 5, the plunger 17 is drawn 100 and preferably considerably slanted backupward and the operation takes place as just wardly. This connecting device or latch 3 described.

is released by the aviator inside the aero Where the tension element is rigid, as in plane as by the treadle, 5 connected to the Fig. 1, or consists of two rigid elements telelatch by a cable 6 passing downwardly and scoping as in Fig.2, I prefer to provide.a.105

rearwardly and then more directly downtorsional spring 22 around the pivot of the wardly over a sheave 7 in the lower part of hinge 2 where the tension element is hinged the aeroplane body. to the aeroplane body; one end 3 of this i The preferred specific construction of the spring engaging a projection 24 a short disreleasable connecting device 3 is better tance back on the tension element, (Fig 2) 11L 5 shown in Figs. 2 and 3. and the other end 25 of the spring engaging Where the flexible tension element '1 is used'as in Fig. 3, a second cable 26 may be provided connected to an eye 27 on the upper end of the bar 14 passing upward andforward over a sheave 28 journaled 1n the lower part of the aeroplane body,.and connected to the rear end of a long tension spring 29 which has its forward end connected to a lug 30 fixed in the lower part of the aeroplane body Thus, the connecting device 3 is pulled up as soon as itis re leased from the stake 4, and the flexible ten sion element 1' is carried with it up close to the bottom of the aeroplane body.

In any instance, it will beseen that the aviator is enabled to get away without the assistance of others to hold the aeroplane back afterhe has started the motor and during the time the motor is gaining speed and the aviator is attending ,toother matters which must be attended to after the starting of the motor and before actualstarting of the aeroplane, in order to insure the safety of i the craft and its occupants.

Having fully described my invention, what I claim as new and desire to secure by Letters Patent is:

1. In anaircraft anchor, elongated tension means having one end part hinged to the craft, and extending rearwardly and downwardly, a manually releasable fastener on the opposite end part of said'tension means, and means for automatically swinging said tension meansup toward the craft when said fastener is released.

2. In an aircraft anchor, a tension element, means to connect one end of said elebers, a pointer on the other member to indicate by said scale the pull of said craft on said retaining element, one of said means for connecting said retaining element being releasable during any position of said pointer along said scale, and means extending from said releasable means inside-the craft and accessible inside said craft for releasing said connecting means.

4. In an aircraft anchor, a retaining element comprising a tubular-member, and another member sliding in the tubular mem bar, a tension spring connecting this other member'to the tubular member inside said tubular member, this other member carrying a pointer, and said tubular member having a slot through which said pointer ex tends, and a series of graduations along said slot to indicate thedegree of extension of said members, a hinge connecting one end of one of said members to an under side of said craft, a torsional spring insaid; inge having one end engaging said member, and

the other end engaging said craft to normally hold said retaining element up close to said craft, a bar fixed on the end of the other one of said members of said retaining element and extending up toward said craft. therefrom, aws eXt-endmg from said bar, an eye fixed to the ground and lymg between said jaws, a plunger sliding through one of said jaws into said eye, a helical spring around said plunger along the upper part of said bar, a lug near the upper end of said bar, a collar fixed on said plunger, said heli, cal spring being compressed between said collar and said lug and yieldably holding said plunger in said eye, said plunger extending through said lug and having an eye therea-bove, a cable fixed in said eye and extending up into the body of said craft, and manipulating means inside'said craft with the other end of said cable attached thereto, whereby said plunger may be withdrawn by an operator inside said craft.

EDWARD H. J UN GCLAS.

Witnesses:

JAMES N. RAMSEY, CLARENCE PERDEW. 

